Steering and braking device



J. W. TATTER STEERING AND BRAKING DEVICE July 14, 1931.

2 Sheets-Sheet l Filed Sept. 1l. 1929 INVENTOR.

A TTORNEYS.

July 14, 1931. J, w, TA1-TER 1,814,576

STEERING AND BRAKING DEVICE Filed sept. 11. 1929 2 sheets-sheet 2 'l a l Patented July 14, k1931 UNITED STATES PATENT OFFICE TOEIN W. TATTER, OF CHICAGO, ILLINOIS, ASSIGNOR TO LEWIS DIFFERENTIAL COM- PANY, OF CHICAGO, ILLINOIS, A CORPORATION OF ILLINOIS STEERING AND BRAKING DEVICE Application led September 11, 1929. Serial No. 391,782.

This invention relates to steering and braking devices, and is particularly adaptable for use in conjunction with the landing gear of aeroplanes for controlling the operation of the plane while on the ground.

Heretofore, in turning or otherwise maneuvering a plane into desired position on the ground, it has been necessary to increase the speed of the engine until the force of the \air from the propeller directed against the rudder is suli'icient to swing the tail ofthe plane around lthe desired amount, or to increase the speed of theplane until the air pressure on the rudder is suiiicient to swing the tail around.

By employing lthe present invention, the speed of the engine and propeller need be only sutiicient to move the planeover the ground, the rotation of the wheels, comprising the landing gear of the plane, being controlled by suitably constructed and arranged elements embodying my invention, and by the operation of which, theplane may be turned to the right or left, or may be gradually slowed down and brought to a stop.

One object of the present mvention is to provide a novel andeiiicient brake mechanism for aeroplanes.

Another object of the invention is to provide a novel and eficient steering device for aeroplanes.

Another object of the invention is to provide a novel construction and arrangement whereby eiiicie'nt braking and steering mechanism may be combined in a unitarystructure which may be conveniently positioned and operated by suitable means for controlling the movement ofanaeroplane while on the ground.

A further object of the invention is to providepa structure wherein the braking and steeringmeans employed for controlling the movements of the plane when on the ground are operatively related with certain of the means for controlling similar movements of the plane when aloft.

A still further object of the invention is to improve devices of the character disclosed in sundry details hereinafter described and Fig. 4 is a transverse sectional elevation of 'a portion of the operating mechanism taken on the line 4 4: of Fig. 2;

Fig. 5 is a group of elements comprising a cam operated piston assembly;

Fig. 6 is an elevational view of a type of brake drum adapted to be secured to the wheels of the landing gear, and also a friction element operativelyrelated thereto, the

view illustrating diagrammatically a Huid pressure operated device for actuating the friction element;

Fig. 7 is a side elevational view of a portion of the manually operated -means for controllingl the operation of the brake and steering mechanism, and also' for controlling the movements of a plane'when aloft, the structure illustrated being viewed as indicated by the arrow in Fig. 1; v

Fig. 8 is a rear elevational view of a portion of the structure illustrated in Fig. 7; and

Fig. 9 is a side elevational view of the structure illustrated in Fig. 7 showing certain of the parts in changed position.

In the illustrative embodiment of the invention shown in the drawings, the aeroplane structure is designated as a Whole by the reference character 10, and includes a fuselage 11 having landing gear struts'l2 and 13 mounted thereon. At the lower ends of the respective struts are rotatably mounti bered member 19 having pistons 2O mounted 'therein and operatively connected by means of links 21. to the ends of the friction elements or shoes 18, the chamber of member 19 being adapted to receive fluid under pressure through a tube 22 in a manner to move the pistons 20 outwardly or away from each other for expanding the friction element 18 into engagement with the drum 17.

The brake mechanism illustrated in Fig. 6 is typical of the structure applied to the wheels 14 and 15, and in the present structure, the tube 22 is illustrated as supplying fluid under pressure to the brake mechanism operatively related to the wheel 14, while the brake mechanism associated with the wheel 15 is supplied with fluid pressure by a tube 23 (Fig. 1).

For actuating the plungers 20 in the chambered member 19, a housing 24 is suitably mounted in the fuselage of the plane, and provided, as shown for illustrating purposes, in the present instance, with a pair of .pressure chambers or cylinders 25 and 26 of substantially identical structure, the open end of each cylinder or chamber being closed by a sealing cup 27, preferably of resilient flexible material, adapted to be secured to the housing 24 by means of rings or members 28 and 29 shown in the present instance as providing end extensions of the housing 24 and serving as guides for hollow pistons 3() and 31 operatively related to the sealing cups 27 and the pressure chambers or cylinders 25 and 26, respectively.

Suitably mounted on the rings-or members 28 and 29, preferably adjacent theN outer faces thereof are plates 32 having outwardly extending bosses 33 formed thereon in which are mounted shafts 34 and 35, Ato theinner ends of which are connected cam members 36 and 37 adapted to extend into the interior of the respective pistons 30 and 31 positioned ,within the rings 28 and 29 mounted on the end portions of the housing 24.

. The piston and cam assembly operatively related to the respective cylinders 25 andl 26 are substantially identical in structure and a description of one will suffice for both.

Referring particularly to Figs. 2, 3, 4, and 5, it will be noted that the pistons 30 andl 31 are of hollow construction having radially formed in the walls thereof and adapted to receive a bearing pin 39, on the opposite ends of which, outside the pistons, are mounted piston blocks 40 adapted to slidably engage oppositely disposed longitudi-' nally extending grooves 41 formed in the linner faces of the rings or piston guide members 28 and 29 in a manner to slide longitudinally therein and at the same time prevent rotation of the pistons 30 and 31 within the guide members 28 and 29. Rotatably mounted onV the piston pin 39 within the walls of the pistons are anti-friction rollers 42 adapted to be engaged by inclined cam surfaces 43 of thel cams 36 and 37 when the latter are rotated as hereinafter described.

For supplying fluid under desired or predetermined Apressure to the chambers or cylinders 25 and 26, and to the' pressure fluid operated means 19, a fluid reservoir 44' (Fig. 1) may be suitably mounted in the fuselage of the plane and provided with tubes or conduits 45 and 46 communicating with the interior of the chambers or cylinders 25 and 26', respectively, the conduits 45 and 46 being provided, in the present instance, with T-littings 47 and 48, adapted to receive the tubes 22 and 23, respectively, by means of which communication is established with the pressure operated means 19 related to the Wheels 14 and 15 of the landing gear.

For exerting sufficient pressure on the fluid within the system to insure efficient operation of the device, a plunger 49. mounted in the fluid reservoir 44 may be lof* moved downwardly within the reservoir by rotating a hand wheel 50, thereby compressing the fluid uniformly throughout the system of chambers and tubing suflicient to place the friction elements or brake shoes 18 in desired position with respect to the brake 'drums 17, but not sufficient to move `fthe friction elements into engagement with the drums, after which valves 52 and 53 positioned in the conduits 45 and 46, respectively, may be closed to hold the predetermined' o'r initial pressure within the system.

For actuating the pressure operated'friction elements 18, bell crank levers 54 and 55 are provided and shown, in the present instance, as pivotally mounted on the upper end portions of levers 56 and 57 journaled at their lower end portions on the bosses 33 in a manner to rotate freely thereon, the levers 56 and 57 being provided with cables 58 and 59, or other suitable means, adapted to be connected with the rudder of the aeroplane for controlling the movements of the plane when aloft, and, when desired, for assisting in controlling the movement of the plane when on the ground.

Mounted adjacent the upper ends of the levers 56 and 57 preferably coincident with extending oppositely disposed apertures 38l Athe pivotal center of the bell crank levers 54 and 55 are outwardly extending rods or bars 60 and 61 adapted to be engaged by the toe portion of the aviators foot as illustrated `in Fig. 8 for manipulating the rudder to which are secured the cams 36 and 37.

For slowing down or bringing the plane to a stop after it has landed, the operation of the device is substantially as follows: Assuming that the system, comprising the chambers 25 and 26, tubes 22 and 23, and the chambered members 19 associated with the brake mechanism on the wheels 14 and 15, is filled with fluid under relatively slight pressure in the manner above described, the aviator or pilot of the plane,by exerting pressure simultaneously on the heel engaging stirrups 62 and 63, may rock the bell crank levers about their pivotal connections with the levers 56 and 57, and through their connections with the links 64 and 65, and

.27 and restricting or reducing the capacity of the chambers 25 and 26 which will force the Huid from the chambers into the tubes 45 and 46 and thence through the vT-fittings 47 and 48, tubes 22 and 23 to the member -19 for moving the pistons 20 and links 21 out-' wardly in a manner to expand the friction elements or brake shoes 18 simultaneously into engagement with the drums 17 mounted on the wheels 14 and 15 of the landing gear, thereby retarding rotation of both the wheels 14 and 15 in a manner common in brake structure, tlglsslowing down the plane or bringing it to a `complete stop.

If, however, the pilot desires to taxi the plane and maneuver it to the right or left to obtain a desired position on the field, this may be done in the following manner: Assuming that a right turn is desired, the aviator or pilot, by exerting heel pressure on the stirrup 62 only of the bell crank lever 54, may rock the lever about its pivotal connection with the lever 56 as indicated by dotted lines in Fig. 7 land through its connection with the link 64 and arm 66,

rotate the shaft 34 in its bearing, thus caus-l ing the cam 36 to rotateand move the pisthe tubing 45, T-tting 47 and tube 22 into the member 19 for expanding the friction element18 into engagementwith the drum 17 associated with the wheel 14, thus retarding or creating a drag on the wheel 14, and, by reason of the fact that the wheel 15 is permitted to rotate freely, causing the, body ofthe plane to swing about the wheel 14 as a center. When the desired position of the plane -is attained in this manner, the pressure on the stirrup 62 may be released permitting the piston 30 toy assumeits normal position whereupon the plane may be taXied in a straight-away directionr as desired.

A left hand turn may be accomplished in a similar manner by exerting heel pressure on the stirrup 63, thereby rotating the cam 37 and moving the piston 31 inwardly with respect to the cylinder 26 for actuating the brake mechanism associated with the landing wheel 15.

If desired, the turning movements ofthe plane may be accelerated by manipulating the rudder of the plane, as for example, in making a left turn, in addition to exerting heel pressure on the stirrup 63 for retarding the rotation of the landing wheel 15, pressure may also be exerted on the rod 61, thereby rocking the lever 57 on its pivotal connection with the boss33, to the position shown in Fig. 9, and through its associated cable 59 swinging the rudder of the -plane to a position where any pressure against the face of the rudder will tend to turn the plane to the left. Obviously, a similar pressure exerted simultaneously on 'the stirrup 62 f and rod 60 will accelerate the movement of the plane in making a right turn.

It will be observed from the foregoing description that the present invention provides a novel construction whereby a plane may be slowed down or brought to a stop after landing, and wherein suitable means and. rudder operating means may be simultaneously actuated for accelerating the turning or steering movements.

Obviously, the present invention is not limited to the precise construction and arrangement shown and described as the same may be variously modified. Moreover, all the features of the invention need not `be used conjointly as the same may be used with advantage in variously different combinations and. sub-combinations. Y

- Having thus described my invention, it is obvious that various immaterial modifications may be made in the same without departing from the spirit of mv invention:

hence, I do not Wish to be understood as limiting myself to the exact form, construction, arrangement, and combination of parts herein shown and described or uses mentioned. l 'f What I claim as new and desire to secure by Letters Patent is:

1.. In a device of the class described, 'thecombination of a plurality of brake drums, brake elements operatively relatedthereto,

a plurality of fluid pressureoperated means for actuating said elements, a housing having a plurality of chambers formed therein communicating respectively With said pressure operated means, meansv for supplying fluid under pressure to said chambers and pressure operated means, and manually operated means for selectively increasing the pressure in one or another or all of said chambers for actuating said brake elements.

2. In a device of the class described, the

combination of a pair of brake drums, brake elements operatively related thereto respectively, a plurality of Huid pressure operated means for,actuating said elements, a housing having chambers formed therein communicatin respectively with said pressure-operated means, means for supplying fluid' under substantially uniform pressure to said chambers and pressure operated means, means for controlling the degree of pressure of the iuid, and manually operated means for selectively increasing the pressure in 'one or another or both of said chambers for actuating said brake elements, said last mentioned means comprlsmg plungersf luid under pressure to said cylinders and pressure operated means, pistons operatively related to said cylinders, and manually operated means comprising cams operatively related to the respective pistons for selectively actuating one or more of said pisL tons to increase the pressure in one'or more of said cylinders for actuating one orimore of said brake elements.

4. In a device of the class described, the combination of a plurality of brake drums,

lbrake elements operatively related thereto,

i a plurality of iuid pressure operated means for actuating said elements, a housing having a plurality of cylinders formed therein ments.

pendently of each other, and manually operated. means for selectively rotating one or more of said cam membersto actuate one or more of said pistons in a manner to increase the pressure in one or more of said cylinders for actuating one o r more of said brake ele- 5. In a steering and braking device for aeroplanes, the combination of 'a plurality of brake drumssecured respectively to the landing Wheels of( an aeroplane, brake elementsgoperatively related respectively to said drums, fluid pressure operated means for actuating said elements respectively, a

housing having a plurality of chambers formed thereinqcommunicating respectively With said pressure operated means, means for supplying fluid under pressure to said chambers and pressureY operated means, means mounted on said housing and operatively related to the rudder of the aeroplane,

means mounted in said housing for increasing the pressure in said chambers, and means mounted on said rudder `operating means for actuating said pressure increasing means.

6. In a steering and braking device for aeroplanes, the combination of a plurality of brake drums secured respectively to the landing Wheels of an aeroplane, brake elements operativelyrelated respectively to said drums, fluid pressure operatedmeans for actuating said elements respectively, ahousing having a plurality of chambersY formed therein communicating respectively With said pressure operated. means, means for supplying fluid under substantially uniform pressure to said chambers and pressure operated means, a plurality of levers mounted`on saidL housing and operatively related to the rudder of the aeroplane, means mounted in said housing for increasing the pressure in said chambers, and independently operated means mounted on said levers for actuating said pressure increasing means. i

7. In a steering Iand braking device for aeroplanes, the Acombination of a plurality of brake drums secured respectively to the landing Wheels of an aeroplane, brake elements operatively related respectively to said drums, Huid pressure operated means for Aactuating said elements, respectively, a housing having a pluralitypof pressure cylinders Vformed ,therein communicating respectively with means, means for supplying fiuid under substantially uniform pressure to said cylinlio said pressure operated' say ders and pressure operated means, pistonsr` mounted 1n said cylmders, cams mounted in said housing and operatively related to said pistons Jfor moving them longitudinally of said cylinders, levers mounted on said housing and operatively related to the rudder of ythe aeroplane, independently and manually operated means mounted on said levers for actuating one or another or all of said cams for increasing the pressure in one or another or all of said cylinders in a manner to apply said brake elements to one or another or all of said brake drums mounted on the landing Wheels of the aeroplane.

8. In a device of the class described, the combination of a plurality of brake drums, brake elements operatively related thereto, a plurality of fluid pressure operated means for actuating said elements, a housing having a plurality of aligned chambers formed therein communicating respectively with said pressure loperated means, means for supplying Huid under pressure to said chambers and pressure operated means, and many ually operated means rotatably mounted in said housing for selectively increasing the pressure in one or another or all of said chambers for actuating said brake elements.

9. In a device of the class described, the combination of a pair of brake drums, brake elements operatively related thereto respec-` tively, a plurality of fluid pressure operated means for actuating said elements, a housing having oppositely disposed aligned chambers formed therein communicating respectively With said pressure operated means, means for supplying fluid under substantially uniform pressure to said chambers andA to said pressure operated means, means for controlling the degree of pressure of the'A fluid, and manually operated means mounted adjacent opposite ends of said housing and rotatable therein forselectively increasing the pressure in one or another or both of said chambers'for actuating said brake elements.

In Witness whereof, I hereunto subscribe my name this 3rd day of September, A. D.

JOHN W. TATTER. 

